Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade

Patent metadata

Field	Value
Publication number	US-9562437-B2
Application number	US-201313871655-A
Country	US
Kind code	B2
Filing date	Apr 26, 2013
Priority date	Apr 26, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.

First claim

What is claimed is:

1. An airfoil of a turbine blade, the airfoil having an external wall surface and comprising:
a leading edge and a trailing edge;
a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges;
an internal cavity;
one or more isolation trenches in the external wall surface;
a plurality of film cooling holes arranged in cooling rows, each film cooling hole having an inlet connected to the internal cavity and an outlet opening onto the external wall surface; and
a plurality of span-wise surface connectors interconnecting only the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes, wherein the span-wise surface connectors in at least one selected row of interconnected film cooling holes are defined in one of the one or more isolation trenches, and the one of the one or more isolation trenches is formed over a length of the at least one selected row of interconnected film cooling holes.

2. The airfoil of claim 1 , wherein the plurality of rows of interconnected film cooling rows comprises at least three rows of interconnected film cooling holes, a first row of the at least three rows of interconnected film cooling holes comprising a first plurality of interconnected film cooling holes extending in a span-wise direction of the airfoil and located substantially along a stagnation line of the leading edge, the at least three rows of interconnected film cooling holes further comprising:
a second row comprising a second plurality of interconnected film cooling holes extending in a span-wise direction of the airfoil and in the pressure sidewall at the leading edge; and
a third row comprising a third plurality of interconnected film cooling holes extending in a span-wise direction of the airfoil and in the suction sidewall at the leading edge, wherein the plurality of span-wise surface connectors interconnecting only the outlets of the film cooling holes in at least the second row are defined in the one or more isolation trenches.

3. The airfoil of claim 2 , wherein the plurality of span-wise connectors interconnecting only the outlets of the film cooling holes in the second and third rows are defined in the one or more isolation trenches.

4. The airfoil of claim 1 , wherein each span-wise connector extends in a span-wise direction only between a pair of outlets of sequential film cooling holes within the same cooling row.

5. The airfoil of claim 1 , wherein the at least one isolation trench comprises a wedge-shaped groove having a depth that decreases in a downstream direction.

6. The airfoil of claim 1 , wherein the plurality of span-wise surface connectors interconnecting only the outlets of the film cooling holes in a single selected cooling row are defined in a single isolation trench.

7. The airfoil of claim 1 , wherein the plurality of span-wise surface connectors interconnecting only the outlets of the film cooling holes in more than one selected row are defined in a single isolation trench.

8. The airfoil of claim 1 , wherein the one or more isolation trenches in the external wall surface are at the leading edge of the airfoil, spaced apart from the leading edge of the airfoil, or both.

9. The airfoil of claim 8 , wherein the one or more isolation trenches in the external wall surface that are spaced apart from the leading edge of the airfoil are in the pressure sidewall, the suction sidewall, or both.

10. A film cooling system for a component having an external wall surface to be cooled, the system comprising:
one or more isolation trenches in the external wall surface;
a plurality of film cooling holes in the component, the plurality of film cooling holes arranged in cooling rows and each film cooling hole having an inlet configured to receive cooling air and an outlet, the outlet opening onto the external wall surface;
a plurality of span-wise surface connectors that interconnect only sequential outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes, the span-wise surface connectors in at least one selected row of interconnected film cooling holes defined in one of the one or more isolation trenches, and the one of the one or more isolation trenches is formed over a length of the at least one selected row of interconnected film cooling holes and extends beyond a footprint of the at least one selected row of interconnected film cooling holes.

11. The film cooling system of claim 10 , wherein the component comprises a turbine blade airfoil having a leading edge and the plurality of rows of interconnected film cooling holes comprises at least three rows of interconnected film cooling holes, a first row of the at least three rows comprising a first plurality of interconnected film cooling holes extending in a span-wise direction of the turbine blade airfoil and located substantially along a stagnation line of the leading edge, the at least three rows of interconnected film cooling holes further comprising:
a second row comprising a second plurality of interconnected film cooling holes extending in a span-wise direction of the turbine blade airfoil and in the pressure sidewall at the leading edge; and
a third row comprising a third plurality of interconnected film cooling holes extending in a span-wise direction of the turbine blade airfoil and in the suction sidewall at the leading edge.

12. The film cooling system of claim 11 , wherein the at least one selected cooling row comprises the second row or the second and third rows.

13. The film cooling system of claim 10 , wherein the one or more isolation trenches comprises a wedge-shaped groove having a depth that decreases in a downstream direction.

14. The film cooling system of claim 10 , wherein the one or more isolation trenches comprise a single isolation trench for each selected row of interconnected film cooling holes.

15. The film cooling system of claim 10 , wherein the plurality of span-wise surface connectors in more than one selected cooling row are defined in a single isolation trench of the one or more isolation trenches.

16. The film cooling system of claim 10 , wherein each span-wise connector extends in a span-wise direction only between the outlets of the selected pair of the film cooling holes, the selected pair of the film cooling holes comprising sequential film cooling holes within the same cooling row.

17. A method for forming an improved film cooled component having an external wall surface, the method comprising the steps of:
forming one or more isolation trenches in the external wall surface;
forming a plurality of film cooling holes in the external wall surface and arranged in cooling rows; each film cooling hole having an inlet connected to a source of coolant and an outlet opening onto the external wall surface;
forming a plurality of span-wise surface connectors in the external wall surface for interconnecting only the outlets of the film cooling holes within the same cooling row to form a plurality of rows of interconnected film cooling holes, wherein the span-wise surface connectors in at least one selected row of interconnected film cooling holes are defined in one of the one or more isolation trenches, and the one of the one or more isolation trenches is formed over a length of the at least one selected row of interconnected film cooling holes.

18. The method of claim 17 , wherein the improved film cooled component comprises an airfoil of a turbine blade and the step of formin

Assignees

• Honeywell Int Inc

Inventors

• Kollati Vighneswara Rao
• Srinivasan Balamurugan
• Liu Jong
• Crites Daniel C
• Tapia Luis
• Malak Malak Fouad
• Rana Rajiv

Classifications

• F05D2230/10

  by removing material · CPC title

• B23P15/02

  turbine or like blades from one piece · CPC title

• F05D2240/306

  related to the suction side of a rotor blade · CPC title

• Y10T29/49341

  with cooling passage · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title